Control of drone-load system method, system, and apparatus

ABSTRACT

Disclosed are systems, apparatuses, and methods to enhance control of a drone-load system, including through drone thrusters or load thrusters.

FIELD

This disclosure is directed to improved systems and methods for and related to control of drone-load system, including a load carried by a drone.

BACKGROUND

Loads may be transported as a load secured to or suspended from an aerial drone or another carrier. When drones or other carriers transport a load, the load may be secured tightly to the drone, such that the two do not have significant independent motion or the load may be suspended below the drone on a suspension cable.

During such operations, a center of mass of the load may be unknown or difficult to obtain prior to take-off. During such operations, the center of mass of the load and or of a drone-load system may change during the operation, such as if the load is suspended on a cable and if the load swings or if a mass within the load shifts. Shifting of mass within a load can severely and detrimentally complicate control a drone-load system, whether the load is suspended on a cable or is tightly secured to the drone. In addition, the center of mass of the drone-load system changes as the load is delivered. In addition, during such operations, loads and drones are subject to winds and other external and internal factors that may cause the load and the drone-load system to move in an unstable or hazardous manner or which may complicate delivery of the load to a target.

Weight and volume of equipment in and carried by a drone must be reduced to reduce fuel consumption, increase speed, increase load capacity, and the like.

During an operation in which a load is carried by a drone or another carrier (carriers comprise helicopters, fixed wing aircraft, cranes, or the like), whether the load is suspended on a cable or is tightly secured to the carrier, observed motion of the suspended load and of the carrier may include the following components: vertical translation (motion up and down) along the Y axis (referred to herein as “vertical translation”), horizontal translation along either or both the X and Z axis, rotation or “yaw” about the Y axis, roll (rotation about the X axis), and pitch (rotation about the Y axis). Roll and pitch may occur primarily with respect to a drone or other aerial carrier and a tightly secured load but may also occur with respect to a suspended load. Horizontal translation can manifest as lateral motion or as conical pendulum motion of one or both of the load and the carrier, with the pivot point of the pendulum being between the load and the carrier (“pendular motion”); pendular motion generally also includes a component of vertical translation. Pendular motion primarily occurs with respect to suspended loads, though it can also affect the carrier or the carrier-load system (also referred to herein as a “drone-load system”).

In addition, when a drone or other carrier transports a load which is a significant percentage (e.g. greater than 1%) of the mass of the carrier and the carrier is not securely anchored to the ground, such as in a drone-load system, momentum transfer between the carrier and the load or changes in the center of mass of the drone-load system may result in an observable change in rotation, position, or velocity of either the drone or the load, even when there may be net conservation of momentum in a system comprising both objects.

Motion in a drone-load system may be effected by movement of the suspension cable, pulling in (contraction) or paying out (extension) the suspension cable, by movement of the drone (e.g. caused by thrusters of the drone or by forces acting on the drone), movement of the load, movement of a center of mass of the load, differences in momentum between the load and the drone, transfer of momentum between the carrier and the load, changes in the center of mass of the drone-load system, as well as by wind—including propeller wash and environmental wind—impacts, and external forces.

Yaw, vertical and horizontal translation, and pendular motion can complicate lift and delivery operations, interfere with operation of control systems, can result in non-linear control dynamics which result in mission failure, cause delays, damage equipment, and may result in injury or death of people on the ground. Yaw, vertical and horizontal translation, and pendular motion can also interfere with bringing a load into or delivering a load to a location. For example, delivery of a load to a location may be significantly complicated by pendular motion or yaw of the load, even if the location is stable and is not also subject to heave, roll, or pitch, as it may be. One or more components of undesired motion of the load may accelerate or grow more pronounced if a suspension cable shortens, such as if a load is drawn up to a drone. Paying out of a suspension cable may result in the carrier gaining elevation, while shortening the suspension cable may result in the carrier descending, either of which may not be a desired result. Vertical translation, horizontal translation, and pendular motion of a load and of a carrier may produce momentum transfer and may interact with a control system of the drone to produce unpredictable and potentially dangerous quasi-oscillatory interaction between the load and the drone (“quasi-” in the sense that the natural frequency of the system may not normally include the response of the drone's control system to forces from of the load).

In addition, some suspended load and delivery operations may involve an obstacle, such as a tree, building, bridge, overhang, or an environmental condition, such as wind, that may interfere with one or more of the carrier, load, and/or suspension cable. It may be desirable to move the suspended load relative to such an obstacle, or for other reasons, in a manner which does not involve the load hanging at a lowest energy position below the drone.

In addition, carriers, including drones, may operate or work with multiple pieces of equipment. One such piece of equipment may be a carrier hoist system. The hoist system on a carrier may be used to lift an object, such as a person, litter, load, or the like from the ground to the carrier, above, or vice versa; this may be referred to as a hoist operation. Hoists may also be used to lift a package to the drone and may hold the package to the drone. In addition, multiple pieces of equipment may be used to aid or support the package delivery or drone-load operation, such as weight scales, package delivery equipment, package slings, a fans proximate to the load, a jungle penetrator, rescue stokes, rescue litter, hose, or other load. If used, such equipment may need to be controlled, which may not be possible, may be inconvenient, or may not be fast enough to respond to circumstances of the drone-load system.

Mechanical and logical complexity of equipment used in drone-load operations is increasing. For example, equipment may perform services for the load and or for the drone; for example, the weight of a load may need to be measured before it is picked up; for example, a hoist may reel in or pay out suspension cable; for example, batteries in the carrier may need to be recharged or replaced, and the like.

Lack of integration may require that many such services be provided with the assistance of people or through execution of additional processes. Performance of such services may not be possible, may be costly, inconvenient, distracting, or dangerous, whether to such persons or to others or property in the vicinity. Inadequate integration between drones and other systems may result in, for example, prematurely discharged batteries, damage to equipment, damage to transported packages, damage to surroundings, injury, loss of life, and failure to initiate or carry out missions, including failure of life saving missions.

In addition, flight dynamics of a drone or other carrier are made more complex on take-off, during operation, and following delivery of the load due to, for example, changes in a center of mass of the drone-load system, interaction of the drone-load system with the environment, and the like following deposition and/or release of a load at a target.

In addition, a control system for a drone or other carrier which uses a non-linear filter, such as an Unscented Kalman filter, may produce undesirable control output when the load approaches a significant percentage of the mass of the carrier and or when the drone-load system includes fans or other thrusters at or proximate to a load, in addition to thrusters at the carrier.

Operation of drone-load systems may be improved, made less hazardous, or made more likely if apparatuses, systems, and methods are provided to enhanced control of a load-bearing drone, control of a hoist of the drone, control of the load by the drone, and/or enhanced control of the load independent of the drone.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1A is a top oblique parallel projection view of a first example of a drone carrying a load via a suspension cable, wherein at least one of the drone, suspension cable, or load comprise a sensor suite and a real-time localization and control enhancement system (“sensor enhanced control system”), in accordance with an embodiment.

FIG. 1B is a top oblique parallel projection view of a second example of a drone carrying a load via a suspension cable, wherein at least one of the drone, suspension cable, or load comprise a sensor suite and a real-time localization and control enhancement system (“sensor enhanced control system”), in accordance with an embodiment.

FIG. 2 is bottom oblique parallel projection of a detail view of the sensor enhanced control system of FIG. 1, in accordance with an embodiment.

FIG. 3 is a top oblique parallel projection of a sensor suite and a load, in accordance with an embodiment.

FIG. 4 is a front elevation parallel projection of a drone carrying a load and comprising a sensor enhanced control system, in accordance with an embodiment.

FIG. 5 is a bottom oblique parallel projection of a drone carrying a load and a sensor enhanced control system (“SECS”), in accordance with an embodiment.

FIG. 6 is a front elevation parallel projection view of a first example of a drone carrying the load and the sensor enhanced control system (“SECS”) of FIG. 5, in accordance with an embodiment.

FIG. 7 is a side parallel projection view of a second example of a drone carrying the load and the sensor enhanced control system (“SECS”) of FIG. 5, in accordance with an embodiment.

FIG. 8 is a bottom oblique parallel projection view of the second example of the drone carrying the load and the sensor enhanced control system (“SECS”) of FIG. 5, in accordance with an embodiment.

FIG. 9 is a front elevation parallel projection of a drone delivering a load to a target with the aid of an enhanced control system, in accordance with an embodiment.

FIG. 10 is a front elevation parallel projection of a drone carrying a sensor enhanced control system (“SECS”) integrated into a load container, in accordance with an embodiment.

FIG. 11 is a front elevation parallel projection of a drone carrying a sensor enhanced control system (“SECS”) integrated into a load container, in accordance with an embodiment.

FIG. 12 is an isomorphic parallel projection of a drone carrying a sensor enhanced control system (“SECS”) comprising compressed gas thrusters and a load, in accordance with an embodiment.

FIG. 13 schematically illustrates electrical, computer processor, memory, and logical control components of a suspended load control system or sensor enhanced control system and of a remote interface, in accordance with an embodiment.

FIG. 14 illustrates an operational module of a suspended load control system or sensor enhanced control system including multiple modes or command states in accordance with an embodiment.

FIG. 15 illustrates a suspended load control decision and control module of a suspended load control system or sensor enhanced control system in accordance with an embodiment.

FIG. 16 is a top oblique perspective illustration of a long line operation performed by a drone and a sensor enhanced control system (“SECS”).

FIG. 17 is a front elevation parallel projection of a drone comprising a sensor enhanced control system (“SECS”) and carrying a load, in accordance with an embodiment.

DETAILED DESCRIPTION

It is intended that the terminology used in the description presented below be interpreted in its broadest reasonable manner, even though it is being used in conjunction with a detailed description of certain examples of the technology. Although certain terms may be emphasized below, any terminology intended to be interpreted in a restricted manner will be overtly and specifically defined as such in this Detailed Description section.

Unless the context clearly requires otherwise, throughout the description and the claims, the words “comprise,” “comprising,” and the like are to be construed in an inclusive sense, as opposed to an exclusive or exhaustive sense; that is to say, in the sense of “including, but not limited to.” As used herein, the term “coupled,” or any variant thereof means any coupling, either direct or indirect between two or more elements; a coupling between the elements can be physical, logical, or a combination thereof. Additionally, the words, “herein,” “above,” “below,” and words of similar import, when used in this application, shall refer to this application as a whole and not to particular portions of this application. When the context permits, words using the singular may also include the plural while words using the plural may also include the singular. The word “or” in reference to a list of two or more items, covers all of the following interpretations of the word: any of the items in the list, all of the items in the list, and any combination of one or more of the items in the list. References may be made herein to modules, routines, and subroutines; generally, it should be understood that a module or routine is a software program executed by computer hardware and that a subroutine is a software program executed within a module or routine. However, modules or routine discussed herein may be executed within another module or routine and submodules or subroutines may be executed independently (modules or routines may be submodules or subroutines and vice versa).

As used herein, “releasable,” “connect,” “connected,” “connectable,” “disconnect,” “disconnected,” and “disconnectable” refers to two or more structures which may be connected or disconnected, generally without the use of tools (examples of tools including screwdrivers, pliers, wrenches, drills, saws, welding machines, torches, irons, and other heat sources) and generally in a repeatable manner. As used herein, “attach,” “attached,” or “attachable” refers to two or more structures or components which are attached through the use of tools or chemical or physical bonding. As used herein, “secure,” “secured,” or “securable” refers to two or more structures or components which are either connected or attached.

The phrases “in one embodiment,” “in various embodiments,” “in some embodiments,” and the like are used repeatedly. Such phrases do not necessarily refer to the same embodiment. The terms “comprising,” “having,” and “including” are synonymous, unless the context dictates otherwise. As used in this specification and the appended claims, the singular forms “a,” “an,” and “the” include plural referents unless the content clearly dictates otherwise. It should also be noted that the term “or” is generally employed in its sense including “and/or” unless the content clearly dictates otherwise.

As used herein, “thrusters” refers to fans, or propellers, as are found, for example, in electric ducted fans (“EDF”), as well as to compressed air jets, hydrogen peroxide rockets, solid fuel rockets, or other sources of thrust fluid as well as to gyroscopes. As used herein, a “drone thruster” is a thruster which provides thrust to lift and or control a drone. As used herein, a “load thruster” is a thruster located proximate to a load, wherein the load is suspended below a drone or other carrier on a suspension cable.

In various embodiments, as described further herein, sensors of or proximate to one or both of a drone and or a load obtain information regarding the position, orientation, or motion of the drone-load system, including of the drone and of the load. One or more logical control modules obtain the sensor data and fuse the sensor data in a non-linear filter according to a system model of the drone-load system, with feedback from at least one of a functional mode or command state of the control module, a thrust and orientation mapping, or a fan mapping. The system model may comprise, for example, a mass of the drone, a mass of the load, a length between the drone and the load, an inertia of the load, an inertia of the drone, a center of mass of the drone-load system, an impulse force of the load thruster, an impulse force of the drone thruster, a rotational motion of the load, a rotational motion of the drone, a pendular motion of the load, a pendular motion of the drone, a movement of the load over time through an absolute coordinate space, and a movement of the drone over time through the absolute coordinate space.

The logical control modules obtain feedback from the functional mode or command state, such idle, maintain location or position relative to a carrier, maintain location, or position relative to a one or more other drones, maintain location, or position relative to a target location, maintain location, or position relative to a location on the ground, move to a location, move between a first location and a second location, hold position, obstacle avoidance, package drop, or direct control. The logical control modules further decide how to output control based on the functional mode or command state. The logical control modules output control signals to actuators such as drone thrusters, load thrusters, control and or to a hoist.

Together, the sensors, logical control modules, and actuators may be referred to herein as a drone and load control system, drone, and suspended load stability system, or as a sensor enhanced control system (referred to together as, “SECS”).

As described, an SECS may thereby provide enhanced control of a drone, of a load transported or delivered by a drone, of a drone-load system, or control of a load, independent from a drone.

An SECS may determine a mass of a load, a center of mass of one or more of the drone, the load, or the drone-load system, determine if a flight control of a drone-load system may be exceeded, determine relative locations of drone, load, and/or target, determine real time relative movement of these components and locations, output force from actuators to move or control a load, to compensate for momentum transfer, wind, and other movement influences through control of actuators, such as drone thrusts, load thrusts, control surfaces of the drone, and or a hoist of a suspension cable.

Vector thrust force produced by a drone thruster and or a load thruster may be used to counteract yaw and pendular motion of the load, of the drone-load system, may be used to translate a load horizontally or rotate a load, such as to avoid an obstacle or to move a load into an offset position relative to a normal lowest-energy hanging position, or may otherwise be used to control the fine location and orientation of a load, independently from and or in conjunction with the drone.

Consequently, an SECS enhances mission safety and improves performance of drone and load operations, including pickup and delivery of packages by drones.

Reference is now made in detail to the description of the embodiments illustrated in the drawings. While embodiments are described in connection with the drawings and related descriptions, there is no intent to limit the scope to the embodiments disclosed herein. On the contrary, the intent is to cover all alternatives, modifications, and equivalents. In alternate embodiments, additional devices, or combinations of illustrated devices, may be added to, or combined, without limiting the scope to the embodiments disclosed herein.

FIG. 1A is a top oblique parallel projection view of a first example of drone 105 carrying load 115, wherein at least one of drone 105 and or load 115 and or suspension cable 110 comprise a sensor suite and a real-time localization and control enhancement system (“sensor enhanced control system” or “SECS”), in accordance with an embodiment. Together, these components may be referred to herein as drone and sensor enhanced control system 100.

Load 115 may comprise a package ready to be delivered as-is or load 115 may comprise a load frame which holds or contains a package to be delivered. Examples of a load frame are discussed further herein.

Sensor enhanced control system 100 may comprise, for example, a processor and a memory. The processor and memory may be present in the drone-load system, such as in the drone and/or in a unit or housing secured to the load and/or suspension cable 110, such as in sensor suite and/or communications module 225 in or secured to load securement structure 230 (discussed in relation to FIG. 2). The memory may comprise instructions or code for modules such as, for example, operational module 1400 and/or decision and control module 1500. When executed by the processor, these modules may provide enhanced control of drone thrusters and or of load thrusters, as discussed herein.

An example of drone 105 is illustrated herein as a winged aircraft, though in embodiments, drone 105 may have one or more propellers, such as a drone helicopter, quad-copter, tilt-wing craft, or the like. An example of a drone as quadcopter drone 106 is illustrated in FIG. 1B. Drone 105 may comprise drone thrusters, such as vertically oriented drone thrusters, horizontally oriented drone thrusters, and or tiltrotor drone thrusters, as may be used in vertical take-off and landing aircraft.

FIG. 1B is a top oblique parallel projection view of a second example of drone 106 carrying load 115 via suspension cable 110, wherein at least one of drone 106, suspension cable 110, or load 115 comprise a sensor suite and a real-time localization and control enhancement system (“sensor enhanced control system”), in accordance with an embodiment. In addition to elements labeled and discussed in relation to FIG. 1A, FIG. 1B illustrates hoist 120, hoist sensor and controller 125, electronics box 130 and electronics box 135. Hoist 120 may be used to reel in or pay out or extend and contract suspension cable 110 and to thereby change a distance between drone 106 and load 115. Hoist 120 may be used in, with, or by drone 105. Hoist 120 may be controlled by actuators, including motors, in or of hoist sensor and controller 125.

Hoist sensor and controller 125 may obtain sensor information, such as cable length and forces on the hoist from a reel of the hoist, such as by a cable length encoder and or a reel torque encoder of a reel of the hoist.

Hoist sensor and controller 125 may comprise electrical components, including computer processors, computer memory, signal processing, logical components, and actuators, including a reel and other actuators. Such components are also discussed herein in relation to hoist logical components 1080.

In computer memory or in logic embodied in circuits within hoist sensor and controller 125 may be a hoist module. The hoist module may comprise logic to operate hoist 120. The hoist module may obtain data or information, such as from a cable length encoder and reel torque encoder and may provide this data or information to other processes. The hoist module may receive data, information, or instructions from, for example, operational module 1400 and decision and control module 1500. The hoist module may implement instructions, such as to wind in or unwind (or pay out) suspension cable 115, to communicate with other processes, to communicate with sensors, or the like.

Operational module 1400 and or decision and control module 1500 may combine the hoist information with machine-vision information and with other sensor information, such as from an inertial navigation system (“INS”), from LIDAR (possibly a portmanteau of “light and radar” or an acronym for “light detection and ranging”), from ultrasonic proximity sensors, from cameras or other machine-visions systems, and from other sensor input discussed herein to localize a package or load relative to a drone, relative to a target location, or relative to another object, to determine a center of mass of the drone-load system, and the like as discussed herein.

Machine-vision information may be produced through image capture by cameras and object detection of the drone and or load in such images. When integrated with information from cameras, INS, LIDAR systems, localized relative parameter and state information (including distance below a drone, elevation of the load relative to the drone or ground, forces on the suspension cable, relative orientation and position of the carrier, load and/or deployable equipment, and separate heading vectors of drone and load within a localized coordinate system) may be developed with low latency and high reliability. When absolute position or location information is available, such as from GPS or another radio navigation or absolute positioning system, absolute and relative localized information may be integrated. Integration of information from the hoist, machine-vision information, and information from inertial navigation, LIDAR, and/or absolute position systems may be performed using methods that comprise, for example, a Kalman Filter, such as an Unscented Kalman Filter (“UKF”) and state model.

FIG. 2 is parallel projection of a detail view of drone and sensor enhanced control system 100 of FIG. 1 from below, in accordance with an embodiment. Sensor suite and/or communications module 220 and sensor suite and/or communications module 225 may comprise suites of sensors and communications equipment.

Sensors in the sensor suites may comprise, for example, a vector navigation unit, which may include an inertial measurement unit (“IMU”). Sensor suite 110 may further comprise, for example, an inertial measurement system, an orientation measurement system, and an absolute position measurement system. The inertial measurement system (“IMS”) may include 3 degrees of freedom (3DOF) accelerometers, gyroscopes, and gravitational sensors, which may comprise microelectromechanical systems (MEMS) sensors. The orientation measurement system may include a magnometer or magnetometer such as a compass, an inclinometer, a directional encoder, and a radio frequency relative bearing system. The absolute position measurement system may include global positioning system (GPS) sensors.

Sensors may further comprise a proximity sensor, such as a depth camera, or light detection and ranging (LIDAR) system (e.g., rotating or linear), and/or an optical sensor such as one or more cameras, infrared (IR) sensors, and/or distance or depth sensors. Proximity sensors may include ground height sensors. Optical sensors may also provide visual information to a user. This information may be communicated to remote devices by the processor, via a data link cable and/or the wireless transceiver. Proximity and optical sensors may provide modules with 360-degree awareness, to allow modules to determine distance between a sensor and points or objects in the environment, perform collision avoidance through detection of obstacles (e.g., a portion of a tree canopy), altering the course of the drone and or a load. The sensors may also be capable of providing ground (or water) position data to drone operators.

Additional sensors may include a strain sensor to gauge stain on a securement to a suspension cable, on a suspension cable, on a load, on clamps to a load, and the like. Additional sensors may include a rotational encoder or thruster speed sensor which may be incremental or absolute, and a shutdown pin presence sensor.

Sensor suite and or communications module 220 and sensor suite and or communications module 225 may comprise communications equipment, such as wireless systems 1331, such as a wireless transceiver, and or wired systems 1332. Such communications equipment may be used to communicate between sensor suite and or communications module 220 and sensor suite and or communications module 225 and or with other equipment or parties, including remote equipment.

Load securement structure 230 may secure suspension cable 110 to load 115. Load securement structure 230 may contain sensor suite and/or communications module 225.

In embodiments, load securement structure 230 may comprise a clamp, straps, and the like, to secure a load to the drone. An example of such an embodiment is illustrated in FIG. 17, in which drone 106 comprises load-clamp legs 1710, which are clamped or otherwise secured to package 1705.

FIG. 3 is top oblique parallel projection of sensor suite and/or communications module 225, load securement structure 230, load 115, and rotational coupling 335, in accordance with an embodiment. Rotational coupling 335 may be a component of load securement structure 230 or may be a separate component. Rotational coupling 335 may allow load 115 to rotate, without imparting significant rotational forces on suspension cable 110 or on a drone. Rotational coupling 335 may be between load 115 and load securement structure 230 and or between load securement structure 230 and suspension cable 110.

FIG. 4 is a front elevation parallel projection of drone 106 carrying load 115 via suspension cable 110, comprising a sensor suite and a sensor enhanced control system. Hoist 120 may be used by processor and modules, such as operational module 1400 and decision and control module 1500, to provide enhanced control of drone 106, of load 115 transported or delivered by drone 106, or control of load 115, as discussed herein.

FIG. 5 is a bottom oblique parallel projection of drone 106 carrying load 115 and a sensor enhanced control system (“SECS”) with load thrusters 505, in accordance with an embodiment. SECS with load thrusters 505 and components thereof are discussed further in relation to FIG. 6. SECS with load thrusters 505 may be used by processor and modules, such as operational module 1400 and decision and control module 1500, to provide enhanced control of drone 105, of load 115 transported or delivered by drone 106, or control of load 115, as discussed herein.

For example, hoist 120 may be activated to shorten or lengthen cable 110, such as to pick up or deliver a package. In so doing, forces from load 115 on drone 106 change. As discussed herein, operational module 1400 and decision and control module 1500 may continuously determine a center of mass of the drone-load system, as well as other parameters of a system model and respond dynamically to these changes, such as to momentum transfer between the load and the drone and external perturbation, such as to winds or contact by external bodies. Operational module 1400 and decision and control module 1500 may control actuators, including hoist 120, via hoist sensor and controller 125, drone thrusters, e.g. sources of thrust 510A, thrust 510B, thrust 510C, other flight control surfaces, or load thrusters 505, e.g. to drive drone-load system 500 toward a then-current objective, such as one set by a functional mode or command state.

As discussed herein, operational module 1400 and decision and control module 1500 may continuously determine, including on take-off, whether a flight control parameter of the drone-load system is exceeded. For example, a drone with an available thrust from drone thrusters may be able to accommodate a mass of a load and a center of mass of the drone-load system with an available reserve for maneuvering, for overcoming headwinds, addressing tailwinds, and the like. If the load or center of mass of load characteristics of the drone-load system exceed a flight control parameter, operational module 1400 and decision and control module 1500 may end or discontinue a mission. The center of mass of the drone-load system may change as a distance between load and drone changes, as a center of mass of either drone or load changes (e.g. such as when a mass within a load shifts), as the drone may burn fuel, and the like.

As discussed herein, the system model may comprise a mass of the drone, a mass of the load, a length between the drone and the load, an inertia of the load, an inertia of the drone, a center of mass of the drone-load system, an impulse force of a load thruster, an impulse force of a drone thruster, a rotational motion of the load, a rotational motion of the drone, a pendular motion of the load, a pendular motion of the drone, a movement of the load over time through an absolute coordinate space, and a movement of the drone over time through the absolute coordinate space.

As discussed herein, actuators comprise hoists, thrusters (including drone thrusts and or load thrusters), and flight control surfaces. Flight control surfaces may comprise, e.g. wings, rudders, leading edge devices (slats, slots, extensions, droop flaps), trailing edge devices (flaps, flaperons), ailerons, spoilers, vortex generators, wing fences, strakes, chine, and fairings.

FIG. 6 is a front elevation parallel projection view of drone 106 carrying load 115 and SECS with thrusters 505 of FIG. 5, in accordance with an embodiment. SECS with thrusters 505 may comprise, for example, arm 645A and arm 645B. Arms 645 may secure thrusters 540 to, for example, sensor suite and/or communications module 225 in or secured to load securement structure 230. Thruster 540A and thruster 540B are illustrated; a greater or lesser number of thrusters may be used. Thrusters 540 may be fans, propellers, EDF, hydrogen peroxide rockets, solid fuel rockets, and the like. Thrusters 540 may be rotated by motors, such as electric motors, combustion motors, and the like. Thrusters 540 may have a fixed orientation or may comprise a mechanism to adjust an orientation of thrusters 540. Thrusters 540 may be bi-directional (e.g. one fan which may be operated in either direction to produce force vectors in opposing directions) or may comprise two one-directional fans facing, for example, in opposite directions (which may be referred to herein as a “thruster unit”). Thrusters 540 may be activated individually or together, with the same or different power, to produce thrust vectoring or thrust vector control. For example, to produce clockwise yaw (when viewed from above), a thruster in a left side of SECS with thrusters 505 may be activated by itself or in conjunction with a thruster in a right side of SECS with thrusters 505. To produce left-ward lateral translation of SECS with thrusters 505, thrusters on a same side of thruster units may be activated. Simultaneous lateral translation and rotation may be produced or an SECS may be rotated to a desired orientation and thrust then applied by two or more thrusters to move the load laterally relative to the drone.

Rotational coupling 335 (illustrated and discussed in relation to FIG. 3) may allow thrusters 540 and load 115 to rotate without imparting a rotational force or torque on suspension cable 110 or drone 105, as discussed herein.

Battery 650 may provide power to thrusters 540 and/or to sensor suite and/or communications module 225 and/or load securement structure 230. As discussed in relation to FIG. 11, power may be provided by drone 106 via an electrical conduit in suspension cable 110.

FIG. 7 is a side parallel projection view of drone 105 carrying load 115 and comprising SECS with thrusters 505 of FIG. 5, in accordance with an embodiment. Sensor suite and/or communications module 220 may obtain sensor data and/or may communicate with sensor suite and/or communications module 225 in or secured to load securement structure 230.

FIG. 8 is a bottom oblique parallel projection view of a detail of drone 106 carrying load 115 and SECS comprising thrusters 540 and arms 645, in accordance with an embodiment.

FIG. 9 is a front elevation parallel projection of drone 105 delivering load 115 to target 950 with the aid of an enhanced control system, in accordance with an embodiment. In example 900, load 115 is at an angle relative to drone 105. This may be due to wind, relative and differential movement and/or acceleration of drone 105 and load 115, by pendular motion of load 115, by pendular motion of drone-load system 900 and the like. In order for navigation modules in drone 115 to navigate load 115 to target 950, navigation modules in drone 115, e.g. operational module 1400 or decision and control module 1500, may need to compensate for such movement. Sensor suite and/or communications module 225 and/or sensor suite and/or communications module 220 may communicate with processor executing, for example, operational module 1400 or decision and control module 1500, to allow drone 115 and/or navigation modules in drone 105, to understand that load 115 is at the angle relative to drone 105 and/or that load 115 is above target 950 notwithstanding that drone 105 is not. For example, these modules may instruct navigation modules in drone 105 to lower, notwithstanding that drone 105 is not immediately above target 950 though load 115 is. For example, these modules may have instructed navigation modules in drone 105 to compensate the angle between load 115 and drone 105 and may have instructed navigation modules in drone 105 to move to the location illustrated in FIG. 9, in which load 115 is above target 950. For example, these modules may instruct navigation modules in drone 105 to wait until load 115 assumes a lower angle relative to drone 105. For example, these modules may identify that load 115 and drone 105 have developed sympathetic motion or quasi-oscillatory motion, for example, due to transfer of momentum between load 115 and drone 105 and may instruct navigation modules in drone 105 to compensate for such sympathetic motion. For example, these modules may instruct hoist 120 to extend cable 110, to lower load 115 to target 950.

FIG. 10 is a front elevation parallel projection of drone 105 and load thrusters integrated with load container 1005, in accordance with an embodiment. In this example, load thrusters integrated with load container 1005 comprises thrusters 1060. Thrusters 1060 may comprise thrusters, as discussed herein. Thruster 1060A and thruster 1060B are on a first side of SECS integrated with load container 1005, while thruster 1060C and thruster 1060D are on a second side of SECS integrated with load container 1005. One or more of thruster 1060 may be a bi-directional thrust assembly.

Thrusters 1060 may be activated individually or together, as with thrusters in SECS thruster apparatus 505.

Load bearing suspension cable connector 1080A and 1080B may connect load container 1005 to suspension cable 1070, including at rotational coupling 1075. Load 1085 may be within the load container 1005. Battery pack 1090 may provide power to thrusters 1060 and/or to computer processor and memory and other load control system logical components, such as load control system logical components 1301. In an embodiment, power may be provided by one or more batteries in drone 105 via power cable 1070 within, around, or next to the suspension cable.

FIG. 11 is a front elevation parallel projection of drone 105 carrying load thrusters 1110 separate from load container 1105, in accordance with an embodiment. Load thrusters 1110 separate from load container 1105 may be similar to load thrusters integrated into a load container 1005 illustrated in FIG. 10, though may comprise thrusters comprising bi-directional fans or bi-directional thrust units. E.g. thruster 1195A and thruster 1195B may each comprise one fan or propeller, wherein the fan or propeller may operate in either direction; in an embodiment, thruster 195 may comprise one motor and two fans in a bi-directional thrust assembly.

In addition, load thrusters 1110 separate from load container 1105 may comprise rotational load bearing 1115, which may allow SECS 1110 and load container 1105, secured thereto, to rotate separately from suspension cable 1070. Rotational load bearing 1120 may allow force from load container 1105 to be transferred to suspension cable 1070, bypassing load thrusters 1110 separate from load container 1105. In addition to or instead of load bearing suspension cable connector 1080A and 1080B, load thrusters 1110 separate from load container 1105 may be secured to load container 1105 by torque transmitting cable 1125A and 1125B. Torque transmitting cable 1125 may transmit torque of load thrusters 1110 separate from load container 1105 to load container 1105.

FIG. 12 is an isomorphic parallel projection of drone 105 with sensor enhanced control system (“SECS”) 1205 and load 115, in accordance with an embodiment. SECS 1205 comprises compressed gas thrusters. Compressed gas thrusters may comprise vessel 1296A and vessel 1296B. Vessels 1296 may contain compressed gas, such as compressed air. In an embodiment, vessels 1296 may contain a propellant, such as hydrogen peroxide, which may react, burn, combust, including on contact with a catalyst, to produce a thrust fluid, such as water and oxygen. Thrust fluid may exit nozzle unit 1297A and/or nozzle unit 1297B and produce a thrust vector on SECS 1205. Exit nozzle units 1297 may comprise one or more exit nozzles; valves, including electronically controllable valves, may be activated to release thrust fluid through a desired exit nozzle and/or side of an exit nozzle unit, to produce opposing thrust vector(s).

FIG. 13 schematically illustrates electrical, computer processor, memory, and other logical control components of or making up a sensor enhanced control system (“SECS”) 1300 including logical control components 1301, remote interface logical components 1350, and hoist and drone logical components 1380, in accordance with one embodiment.

Logical control components 1301 may be in, for example, a drone housing, in a thruster housing, such as in a housing for a load thruster, in a sensor housing, and the like. Logical control components 1301 and their housing may be separable from a drone, such as when a load sensor or load thruster are separable from the drone.

As illustrated in the embodiment in FIG. 13, within logical control components 1301 may be sensor suite 1305, processor 1320, memory 1325, communication system 1330, output 1315, input 1333, and power management 1340.

Sensor suite 1305 may comprise position sensors 1306, orientation sensors 1307, inertial sensors 1308, proximity sensors 1309, reference location sensors 1310, and thrust sensors 1011.

Processor 1320 may be one or more processor, microcontrollers, and or central processing units (CPUs). In some embodiments, processors and microcontrollers may be mounted to the same printed circuit board (PCB).

Memory 1325 may generally comprise a random-access memory (“RAM”), a read only memory (“ROM”), and a permanent non-transitory mass storage device, such as a disk drive or SDRAM (synchronous dynamic random-access memory).

Memory 1325 may store program code for modules and/or software routines, such as, for example, navigation system 1326 and module instructions, such as, for example, operational module 1400 and decision and control module 1500, as well as data or information used by modules and/or software routines, such as, for example, target data 1327, and mode or command state information 1328.

Memory 1325 may also store an operating system. These software components may be loaded from a non-transient computer readable storage medium into deployable equipment memory 1025 using a drive mechanism associated with a non-transient computer readable storage medium, such as a floppy disc, tape, DVD/CD-ROM drive, memory card, or other like storage medium. In some embodiments, software components may also or instead be loaded via a mechanism other than a drive mechanism and computer readable storage medium (e.g., via a network interface.

Memory 1325 may also comprise a kernel, kernel space, user space, user protected address space, and a datastore. As noted, memory 1325 may store one or more process or modules (i.e., executing software application(s)). Processes may be stored in user space. A process may include one or more other process. One or more process may execute generally in parallel, i.e., as a plurality of processes and/or a plurality of threads.

The kernel may be configured to provide an interface between user processes and circuitry associated with processor 1320. In other words, the kernel may be configured to manage access to processor 1320, a chipset, I/O ports, and peripheral devices by processes. The kernel may include one or more drivers configured to manage and/or communicate with elements of operational components of deployable equipment (i.e., processor 1320, chipsets, I/O ports, and peripheral devices).

Processor 1320 may also comprise or communicate via a bus and/or a network interface with memory 1325 or another datastore.

The data groups used by modules or routines in deployable equipment memory 1325 may be represented by a cell in a column or a value separated from other values in a defined structure in a digital document or file. Though referred to herein as individual records or entries, the records may comprise more than one database entry. The database entries may be, represent, or encode numbers, numerical operators, binary values, logical values, text, string operators, references to other database entries, joins, conditional logic, tests, and similar.

Communication system(s) 1330 may include wireless system(s) 1331 such as a wireless transceiver and wired system(s) 1332. Output 1315 includes thrust control 1316 via thruster controllers. Output 1015 includes hoist control 1313, to control a hoist. Power managing systems 1340 regulate and distribute the power supply from, e.g., batteries. One or more data connectors, data buses, and/or network interfaces may connect the various internal systems and logical components of the deployable equipment. Input 1333 may include commands conveyed through a touchscreen, a joystick, a keyboard, a microphone, a camera, one or more buttons, input from other processes 1303, or the like.

Aspects of the system can be embodied in a specialized or special purpose computing device or data processor that is specifically programmed, configured, or constructed to perform one or more of the computer-executable instructions explained in detail herein. Aspects of the system can also be practiced in distributed computing environments where tasks or modules are performed by remote processing devices that are linked through a communications network, such as a local area network (LAN), wide area network (WAN), the Internet, or any radio frequency communication technology. Data from deployable equipment may be of very low bandwidth and may not be restricted to a frequency or communication protocol. In a distributed computing environment, modules can be located in both local and remote memory storage devices.

Logical control components 1301 may work with a remote positional unit, remote interface, or target node (“remote interface unit”) and logical components thereof, such as remote interface logical components 1350, and or with a hoist and drone logical components, such as hoist and drone logical components 1380, in accordance with one embodiment.

In embodiments, the remote interface unit may, for example, be held by an operator or attached to an object by magnets, bolts, or any other attachment mechanism. In embodiment, the remote interface unit may be dropped at a location on the ground or attached to, e.g., a life preserver or other flotational device, a rescuer, a load to be picked up, at a location for a load to be delivered, or an operational specific location. In embodiments, the remote interface unit may be provided by a mobile phone executing remote interface unit instructions.

In embodiments, remote interface logical components 1350 may convey input from an operator to logical control components 1301, such as command states and operational instructions to operational module 1400. In embodiments, remote interface logical components 1350 may convey information or data from hoist and drone logical components 1380 to logical control components 1301 and or to an operator, such as regarding a status of the drone, of the hoist, of a drone-load system, a length of suspension cable paid out, a force or mass on the hoist from the suspension cable, a center of mass of the drone-load system, a distance between a load and a target location, and the like.

Remote interface logical components 1350 may be in communication with logical control components 1301 and or with hoist and drone logical components 1380 via communication systems 1370, which may be wireless 1371 or wired 1372. Output 1360 from remote interface 1350 may include information displayed on a screen 1361, and audio 1362. Input 1365 to remote interface 1350 may include commands conveyed through touchscreen 1366, a joystick 1367, a microphone, a camera, one or more buttons, input from other processes 1368, or the like. In various embodiments, remote interface 1350 may comprise one or more physical and/or logical devices that collectively provide the functions described herein.

Remote interface logical components 1350 may further comprise processor 1369 and memory 1373, which may be similar to processor 1320 and memory 1325. Memory 1373 may comprise software or firmware code, instructions, or logic for one or more modules used by the remote positional unit, such as remote interface module 1374. For example, remote interface module 1374 may provide control and interface for a remote interface, such as to allow it to be turned on/off, to pair it with a drone, with a load, with hoist and drone logical components 1380, with logical control components 1301, to input instructions, or the like.

In embodiments, remote interface logical components 1350 may comprise a sensor suite or beacon configured to communicate, such as wirelessly, with logical control components 1301 and or hoist and drone logical components 1380 to provide, for example, a position reference. If the logical control components 1301 comprise what is considered a primary sensor suite and may be located at or proximate to a load, a secondary sensor suite location can be the drone, and a tertiary sensor suite location can be a location of interest for the load (e.g., a position to which or from which the load is to be obtained or delivered).

Also illustrated in FIG. 13 are hoist and drone logical components 1380. Hoist and drone logical components 1380 may comprise processor 1381 and memory 1382, which may be similar to processor 1320 and memory 1325. Memory 1382 may comprise software or firmware code, instructions, or logic for one or more modules used by a hoist and drone, such as a drone with a hoist and drone operational module 1302. For example, hoist and drone operational module 1302 may pair a drone and hoist with load thrusters, may output sensor data of the hoist and of the drone to logical control components 1301, and may receive and act on local and remote instructions, such as to retract or extend a suspension cable, to transport a load according to an functional mode or command state, or the like.

Hoist and drone logical components 1380 may be in communication with logical control components 1301 and or remote interface logical components 1350 via communication system 1391, which may comprise wireless 1391 or wired 1392 transceivers. Output 1385 from hoist and drone logical components 1380 may include information or data from, for example, hoist and drone sensors 1384, such as, for example, a cable length encoder, a reel torque encoder, a cable presence sensor (to sense the presence of a suspension cable in a hoist), stain gauges, equipment temperature sensors, power sensors, and the like. Output 1385 from hoist and drone logical components 1380 may further include information or data from, for example, thrusters of the drone, encoders of thrusters of the drone, power controllers of the drone (including batteries, electronic speed controllers, and the like), and the like. Input 1386 to hoist and drone logical components 1380 to control the hoist and drone may further comprise commands from other processes 1389, such as from logical control components 1301 and modules thereof, such as operational module 1400 and decision and control module 1500. Input 1386 to hoist and drone logical components 1380 to control the hoist and drone may come from other processes 1389, such as from remote interface logical components 1350, logical control component 1301, and from human operators, which commands may be conveyed through, for example, such as touchscreen 1387, joystick 1388, a microphone, a camera, one or more buttons, or the like.

FIG. 14 illustrates operational module 1400 of an SECS, in accordance with one embodiment. Instructions of, or which embody, operational module 1400 may be stored in, for example, memory 1325, and may be executed or performed by, for example, processor 1320, as well as by electrical circuits, firmware, and other computer and logical hardware of an SECS with which operational module 1400 may interact.

In block 1405, if not already present in a drone and/or suspension cable, hardware embodying the SECS may be deployed onto a suspension cable from which a load may be suspended. In embodiments, an SECS need not be powered on for deployment.

In block 1410, the SECS may be started up. In some embodiments, the system can be initialized by the press of a button located on or remote from the SECS. Near the external button that can initialize the system, another button may be present that allows for immediate system shut down when pressed. In addition to the initialization interface, operational module 1400 may also be initialized by an operator or process not directly next to the system.

In block 1415, operational module 1400 may be activated.

In block 1416, a functional mode or command state may be initiated, such as according to a selection by an operator or by another process.

In block 1417, which may iterate continuously during operation, including on or before take-off, operational module 1400 may determine whether a flight control parameter of the drone-load system is not exceeded. For example, a system model, further discussed in relation to 1500, may comprise parameters a mass of the drone, a mass of the load, a length between the drone and the load, an inertia of the load, an inertia of the drone, a center of mass of the drone-load system, an impulse force of the load thruster, an impulse force of the drone thruster, a rotational motion of the load, a rotational motion of the drone, a pendular motion of the load, a pendular motion of the drone, a movement of the load over time through an absolute coordinate space, and a movement of the drone over time through the absolute coordinate space. One or more of such system model parameters, or a combination thereof, may be evaluated as a flight control parameter. One or more of such flight control parameters may be evaluated in conjunction with information such as a location of a target, available power to the drone, weather information, and the like, to determine whether the flight control parameter will be exceeded with respect to a then-current objective. For example, if a center of mass of a drone-load system is too far to one side or if a mass of a load, measured in terms of response to the drone-load system to force from thrusters, is too great, an impulse force of a drone thruster may not be sufficient to maneuver the drone-load system.

If affirmative or equivalent at block 1417, at block 1418 operational module 1400 may perform a landing, including an emergency landing. A landing may comprise a descent to a nearest, most open, least populated area.

In block 1420 and a functional mode or command state, operational module 1400 may perform or call suspended load control decision and control module 1500 as a subroutine or submodule, to implement a functional mode or command state. The functional modes or command states of the system are:

Idle mode 1421: all internal systems of the SECS are operating (e.g., the SECS observes its motion and calculates corrective action), but the load thrusters or instructions to the or drone thrusters are shut off or maintain existing speed only, without action to affect motion of a load.

Maintain relative position vs. ownship module 1422: The load is stabilized with respect to a slung origin point. For example, when the SECS with load thrusters is suspended with a load below a drone, maintain relative position vs ownership module 1422 will cause the load thrusters of the SECS to keep the load directly below the drone. Maintain relative position vs ownership module 1422 localizes the drone motion and performs the corrective actions necessary with the thrusters to critically damp any other suspended load motion. If the drone is traveling at a low speed, the SECS with thrusters will couple its velocity with the drone so the two entities move in unison. Upon a disturbance to the load, maintain relative position vs drone module 1422 provides thrust in the direction of the disturbance to counteract the disturbance, eliminating the swing. If the SECS does not have thrusters, (“SECS”), maintain relative position vs ownership module 1422 will interact with the control or navigation module of the drone to counteract or dampen differences between motion of the load and motion of the drone. For example, if the drone and load have developed sympathetic motion relative to one another, such as pendular motion in one or both objects, which pendular motion is offset, maintain relative position vs ownership module 1422 may cause the drone to move in a manner which dampens or reduces such differences in motion.

Move to/stop at position module 1423: In an SECS without load thrusters, move to/stop at position module 1423 will interact with the drone thrusters to stabilize the drone and load to a fixed position, counteracting the influence of the weather or transfer of momentum with the load. This mode has the effect of killing all motion. In an SECS with load thrusters, move to/stop at position module 1423 will activate load thrusters and/or the drone thrusters to stabilize the load and drone to a fixed position, counteracting the influence of the weather or transfer of momentum with the load. This mode has the effect of killing all motion. In either case, an operator or other process can send the desired target position to move to/stop at position module 1423 via, for example, the remote interface 1350. This can be accomplished in at least two ways:

Target node position module 1424: The operator or a recipient of a package can place a remote positional unit or target node 1310 at the desired target location (e.g., target 950 of FIG. 9). The target node or reference 1310 will communicate wirelessly with target node position module 1424 to indicate the desired position or target, and target node position module 1424 responds by maneuvering the drone and/or an SECS with load thrusters to the desired location. A remote interface 1350 UI may receive and display the location information of both entities.

Designated position module 1425: An operator or another process can use a remote interface 1350 to send a designated position (e.g., latitude and longitude coordinates) as a commanded location to designated position module 1425. Designated position module 1425 will then steadily direct the drone and SECS to the desired position. Designated position module 1425 may simultaneously send feedback to the remote interface 1350 regarding position and distance information.

Hold position module 1426: may resist all motion and attempt to maintain a current position of the drone, notwithstanding or in response to external forces, such as weather and motion of the load. If in an SECS with load thrusters, hold position module 1426 may resist all motion and attempt to maintain a current position of the load and or the drone, notwithstanding or in response to external forces, such as weather, independent of the drone's motion. This module has the effect of dampening all motion of the drone or load. This mode has conditional responses relative respectively to drone speed, safety factors, and physical constraints.

Direct control module 1427: Joystick or external process instructed operation of the drone in three degrees of freedom. The operator or an external process is able to directly control positioning, rotation, and thruster output level of either the drone or of load thrusters, with control systems augmented by decision and control module 1500. Though the SECS is entirely closed-loop and does not require external control during operation, there is an option for user or external process control.

Obstacle avoidance mode 1428: identifies a path of the drone-load system, identifies objects in the path, determines position, rotation, thruster output level, and suspension cable length which may avoid the obstacle, and outputs instructions to thrusters and or hoist to avoid the obstacle. For example, obstacle avoidance module 1428 module may receive and process sensor information such as to i) to equalize the distance between sensor locations, such as at fan units and objects, such as obstacles, sensed in the environment or ii) to measure or receive geometry of a load, measure geometry of obstacles sensed in the environment, determine, or receive the position, orientation, and motion of the load, and negotiate the load relative to the obstacle.

Position relative to first and second locations mode 1429: An operator or process can use, for example, remote interface logical components 1350 to designate a first position (e.g., pickup or drop off location); the operator or process may further designate a second location, such as a location of a drone, a location on the ground, etc., and may also designate a desired a rate of change between the first and second locations. Thrusters and hoist are activated to stabilize the drone relative to the first location and then activates hoist and load thrusters to move the load from the first location to the second location. The rate of change may be based on percentage of a maximum rate of change actuators can safely achieve. This mode may further hold a desired tension on a suspension cable.

Package drop 1431: The drone and SECS picks up, transports, and delivers a load, such as a package, to a destination. This may include activation of actuators to release a package, obtaining images of the release location, obtaining other authentication or authorization for the delivery, and the like.

In block 1430, the drone completes its operation and the drone may return to a charging location, dispatch center, or the like.

In block 1435, if the drone comprises collapsible components or components which may be removed, such as thrusters on propulsion arms or a load carrying structure, they may be folded up, released, or other removeable components may be removed. The drone may be stowed in a charger or any convenient location.

At done block 1499, if not performed at block 1435, operational module 1400 may be shut down.

FIG. 15 illustrates decision and control module 1500 of an SECS in accordance with one embodiment. Instructions of, or which embody, decision and control module 1500 may be stored in, for example, memory 1325, and may be executed or performed by, for example, processor 1320, as well as by electrical circuits, firmware, and other computer and logical hardware with which decision and control module 1500 may interact.

Decision and control module 1500 may operate in a closed loop to understand its position and motion in near real time, determine a most desired system response, and send desired response(s) to load thrusters or drone thrusters to control the load or enhance control of the drone during operations. This process may be continuous as long as the system is powered.

At block 1505, decision and control module 1500 may obtain sensor data from, for example, sensors 1305, such as accelerometer, gyroscope, magnetometer, GPS, lidar/radar, machine vision, and/or range finders. Sensor data may comprise image data, accelerometer data, gyroscope data, magnetometer data, light detection and ranging (“LIDAR”) data, and, if available, global positioning system (“GPS”) data. Image data may comprise object detection, such as detection of load, of an SECS, of a drone, as well as components of such an object, such as identification of an arm of a drone, a hoist, a fan unit, or the like. Image data and object detection may also comprise identification of optical flow of such images or pixels in successive frames. Accelerometer data may comprise 3-degree of freedom (“3 DoF”) acceleration data in a sensor coordinate frame. Gyroscope data may comprise 3 DoF angular acceleration data in the sensor coordinate frame. Magnetometer data may comprise 3 Degree of Freedom (“DoF”) magnetic field data in the sensor coordinate frame. LIDAR data may comprise point, sweep, rotating, radial, distance, and/or linear data which measures distance and/or angle relative to objects, the ground, and/or water.

At block 1510, the decision and control module 1500 combines data from the sensors to obtain a data fusion describing position, orientation, motion, and environment of the drone-load system.

Sensor data is fused and filtered by decision and control module 1500 through non-linear flavors of a Kalman Filter to yield an accurate representation of the system's state. Closed-loop control methods including fuzzy-tuned proportional, integral, and derivative feedback controllers have bidirectional communication with advanced control methods including deep learning neural nets and future propagated Kalman filters, allowing for further real-time system identification.

At block 1515, decision and control module 1500 performs state estimation using non-linear state estimators to project near-term future motion based on the data fusion and on feedback from the decision and control engine to the state estimator. In this block decision and control module 1500 may feed a system model and its past estimated or initialization state to a data fusion disturbance estimate model, such as into a system model in an unscented Kalman Filter (“UKF”), to be fused with then-current sensor data. As noted, the UKF and system model may include, and may therefore determine as an estimated state, one or more of a mass of a drone, a mass of load and SECS, a cable length, an inertia of the drone, an inertia of load and SECS, a fan and actuation or impulse force of the drone, a fan and actuation force or impulse force of load thrusters, rotational motion of the drone, rotational motion of the load, pendular motion of the drone, pendular motion of load thrusters or load, movement of a drone over time through an absolute coordinate space, and movement of a load over time through an absolute coordinate space.

At block 1520, decision and control module 1500 takes state estimation 1515, informed by the user-selected functional mode or command state 1520, as well as additional feedback from the thrust and orientation mapping 1530 and output control 1540, and decides how the drone-load system should move or exert force.

Algorithmic output is sent to motion or power controllers, such as ESCs, which will send the desired thrust response to the thrusters and hoist via, for example phase control of pulse modulated power signals. The net thrust output is mapped in real-time through encoders and load cells then sent back to decision and control block 1520 and onward for closed-loop control.

At block 1525, decision and control module 1500 maps desired orientation with thrust vectors from thrusters to generate a thrust and orientation mapping to achieve the determined thrust and orientation of the SECS apparatus.

At block 1530, decision and control module 1500 maps the thrust and orientation mapping to thrusters, thruster thrust vectors, the hoist, and control surfaces and generates a fan, hoist, and control surface mapping to control thrusters, the hoist, and control surfaces to achieve the desired thrust, orientation, and spacing of the drone and load.

At block 1535, decision and control module 1500 applies the fan, hoist, and control surface mapping to output power control signals to actuators such as the thrusters, hoist, and control surfaces (or electronic components controlling the same) of the drone to achieve the determined thrust and orientation, exerting commanded control output and implementing a dynamic response.

In embodiments, a determination to move a load to a desired location may first result in re-orientation or rotation of the load and or drone with respect to the desired location and then thrust to propel the load toward the desired location.

At done block 1599, decision and control module 1500 may conclude or return to a module which may have called it.

FIG. 16 is a top oblique perspective illustration of a long line operation performed by drone 105 and an SECS. Suspension line 1605 extends from a hoist in drone 105. Load thrusters, a sensor suite, and communications modules 1610 (“remote SECS components”) and or suspension line 1605 are secured to load 1615, which may be beneath the remote SECS components 1610. Drone 105 may orbit a target location, with suspension line 1605 contouring a gravity well, and load 1615 generally at the target location. To precisely position and orient load 1615 relative to the target location, the SECS in or of drone 105 may output thrust from load thrusters. The SECS of drone 105 may further control a hoist of drone 105 to control a tension on suspension line 1605 and an elevation of remote SECS components 1610. The SECS of drone 105 may further control thrusters of drone 105 to maintain the orbit or, for example, to transition to transporting load 1615 to another location. Position relative to first and second locations mode 1429 may be used in such an operation.

FIG. 17 is a front elevation parallel projection of drone 106 comprising an SECS and carrying load 1705, forming drone-load system 1700, in accordance with an embodiment. In this embodiment, load 1705 is not carried on a suspension cable or may be secured by a suspension cable which is short; in this embodiment, load 1705 is secured by or between legs 1710 of drone 106. This figure illustrates that load 1705 may have a non-uniform density and that drone 106 and its SECS may, as discussed herein, determine a system state of the drone-load system 1700, including a center of mass of drone-load system 1700, may determine if a flight control of drone-load system 1700 in the system state is exceeded, may instruct actuators of drone-load system 1700 to transport load 1705 to a destination, automatically compensating for states of drone-load system 1700, may deliver load 1705, may resume flight of drone 106 without load 1705, and may automatically re-calculating the system state and actuator control parameters to achieve the then-current objective.

Aspects of the system can be embodied in a specialized or special purpose computing device or data processor that is specifically programmed, configured, or constructed to perform one or more of the computer-executable instructions explained in detail herein. Aspects of the system can also be practiced in distributed computing environments where tasks or modules are performed by remote processing devices that are linked through a communications network, such as a local area network (LAN), wide area network (WAN), or the Internet. In a distributed computing environment, modules can be located in both local and remote memory storage devices.

In some embodiments, the remote positional unit or target node may be a mobile phone or may be a special purpose device made of durable polymer or plastic and may be, e.g., large enough to fit into a hand. The remote positional unit or target node may have an external antenna. The remote positional unit or target node may be secured to a location by magnets, bolts, or any other securement. The remote positional unit or target node may be dropped to a location on the ground or secured to, e.g., a life preserver or other flotational device, a rescuer, a load to be picked up, a location for a load to be delivered, or an operational specific location. The remote position unit or target node may be brought to the location, activated to identify the location, and then may be removed from the location.

The entire process is unmanned and automated aside from the high-level operator-selected or process-selected functional control modes. The net output is a control force to stabilize a suspended load or to enhance control of a drone carrying a load.

Status indicator lights may be mounted on various surfaces of a drone to aid in visibility and operation of the drone from above and below. For example, a drone may have external lighting such as LEDs near the load thrusters as well as drone thrusters that identify the edges and orientation of drone and load. This may allow for improved identification in hard viewing situations such as inclement weather. During operation, the LED display indicators may show that the drone-load system is active and may convey useful information.

Covers may contain and protect computer hardware, such as a computer processor and memory, a power supply, electronic speed controllers, microcontrollers, sensors, and the like, such as load control system logical components 1301 and hoist and drone logical components 1380. A power supply may be a single power brick or an array of battery cells wired in series and/or in parallel, such as lithium-polymer (LiPo) cells. Batteries may be removable for inspection and/or to swap discharged and charged batteries. Batteries may be charged while installed in drone (i.e., without having to remove them) via nodes or a wireless charging system). Batteries may include auxiliary battery(ies) to supply a steady supply of power to a processor even if thrusters draw a relatively large amount of power from main batteries. In embodiments, a drone can provide power through a line extending down the suspension cable to load thrusters, sensors, and the like. In embodiments, the drone can provide some power to equipment, while the equipment may obtain additional power from an on-board power supply.

A drone and components discussed herein may be formed of any suitable material such as metals, plastic, and composite materials, such as fiber reinforced resin. A drone may allow access into internal space via a sealed hatch or one or more removable panels or components, allowing for maintenance and inspection.

Although specific embodiments have been illustrated and described herein, it will be appreciated by those of ordinary skill in the art that alternate and/or equivalent implementations may be substituted for the specific embodiments shown and described without departing from the scope of the present disclosure. This application is intended to cover any adaptations or variations of the embodiments discussed herein. 

1. A control system for a drone-load system to influence at least one of a position, orientation, or motion of the drone-load system, comprising: the drone-load system, wherein the drone-load system comprises a drone and a load, wherein the drone comprises a drone thruster and wherein the load is secured to the drone; a sensor suite, and a computer processor and memory, wherein the memory comprises a control module which, when executed by the computer processor, is to determine at least one of a position, orientation, or motion of the drone-load system based on a sensor data from the sensor suite and is to control the drone thruster to influence at least one of the position, orientation, or motion of the drone-load system.
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 28. (canceled)
 29. (canceled)
 30. (canceled)
 31. (canceled)
 32. (canceled)
 33. (canceled)
 34. (canceled)
 35. (canceled)
 36. (canceled)
 37. (canceled)
 38. (canceled)
 39. (canceled)
 40. (canceled)
 41. (canceled)
 42. (canceled)
 43. (canceled)
 44. (canceled)
 45. (canceled)
 46. (canceled)
 47. (canceled)
 48. (canceled)
 49. (canceled)
 50. (canceled)
 51. (canceled)
 52. (canceled)
 53. (canceled)
 54. (canceled)
 55. (canceled)
 56. (canceled)
 57. (canceled)
 58. (canceled)
 59. (canceled)
 60. (canceled) 